公开(公告)号：US09618021B2

公开(公告)日：2017-04-11

申请号：US14096970

申请日：2013-12-04

Applicant: Airbus Operations GmbH

Inventor： Cihangir Sayilgan ,  Markus Mueller ,  Henrik Linnemann

IPC: B32B41/00 ,  F16B2/12 ,  F16L3/02 ,  H02G3/32

CPC classification number: F16B2/12 ,  F16L3/02 ,  H02G3/32 ,  Y10T403/20

Abstract: An arrangement for attaching a system to a structure having a base element to retain the system, a positioning element to position the base element at a location on the structure and a fixation device to fix the base element at the location on the structure. The base element has a section for holding the system and a section for being clamped to the structure. The clamping section has an element for alignment on the positioning element. The positioning element has a surface for being bonded to the structure and a positioning section for acting together with the alignment element. The fixation device has a counter element with a clamping area for being positioned on an opposite side of the structure from the clamping section and a fastener for clamping the base element and the counter element to the structure. An installation method for such an attachment arrangement is provided.

公开(公告)号：US20150298401A1

公开(公告)日：2015-10-22

申请号：US14522786

申请日：2014-10-24

Applicant: Airbus Operations GmbH

Inventor： Thomas Hoffmeister ,  Markus Mueller ,  M. Ichwan Zuardy

IPC: B29C70/34 ,  B29C70/54

CPC classification number: B29C70/34 ,  B29C33/02 ,  B29C33/48 ,  B29C70/345 ,  B29C70/462 ,  B29C70/54 ,  B29D99/0003 ,  B29L2031/3076 ,  B29L2031/3082

Abstract: A curing tool for a shell component, includes a first tool component, which is cuboid and has a wedge-shaped bevel forming a first sheared edge on a first side edge, and a second tool component, which is cuboid, has a wedge-shaped bevel forming a second sheared edge on a first side edge and has a first corner bevel on a second side edge diagonally opposite the first side edge. The wedge angles of the first and the second sheared edge are equal.

Abstract translation: 一种用于外壳部件的固化工具，包括第一工具部件，该第一工具部件是长方体形的并且具有在第一侧边缘上形成第一剪切边缘的楔形斜面，以及长方体形状的第二工具部件，具有楔形 斜面在第一侧边缘上形成第二剪切边缘，并且在与第一侧边缘对角地相对的第二侧边缘上具有第一角部斜面。 第一和第二剪切边缘的楔角相等。

公开(公告)号：US20150083861A1

公开(公告)日：2015-03-26

申请号：US14502670

申请日：2014-09-30

Applicant: Airbus Operations (SAS) ,  Airbus Operations GmbH

Inventor： Sebastien Alby ,  Laurent Giuseppin ,  Markus Mueller

IPC: B64C1/06

CPC classification number: B64C1/061 ,  B64C1/06 ,  B64C1/064 ,  B64C1/12 ,  B64C1/18 ,  B64C3/18 ,  B64C3/182 ,  B64C3/187 ,  B64C2001/0081

Abstract: The invention relates to a structural element for an aircraft fuselage, generally shaped in the form of a longitudinally elongate section. The element comprises two wings, each wing including: a portion that extends uninterrupted along the entire length of the section, and legs spaced apart from one another and extending from said uninterrupted portion such as to define an opening between two consecutive legs. One of the legs of one wing is arranged to face at least part of the opening defined between two consecutive legs of the other wing. Consequently, the structural element can be produced from a single fibrous preform on a curved tool, minimizing waste material and reducing the weight of said element.

Abstract translation: 本发明涉及用于飞行器机身的结构元件，其通常成形为纵向细长部分的形式。 元件包括两个翼，每个翼包括：沿着该截面的整个长度不间断延伸的部分，以及彼此间隔开并从所述不间断部分延伸的腿，以限定两条连续腿之间的开口。 一个翼的一个腿被布置成面对限定在另一个翼的两个连续腿之间的开口的至少一部分。 因此，结构元件可以由弯曲工具上的单个纤维预制件制成，使废料最小化并减轻所述元件的重量。

公开(公告)号：US10053205B2

公开(公告)日：2018-08-21

申请号：US15082530

申请日：2016-03-28

Applicant: Airbus Operations GmbH

Inventor： Claas De Jong ,  Markus Mueller ,  Karim Grase ,  Matthias Jessrang ,  Thomas Konsolke ,  Lars Fiedler ,  Jelle Bloemhof

IPC: B64C1/10 ,  B29C70/20 ,  B29C70/30 ,  B64F5/00

CPC classification number: B64C1/10 ,  B29C70/202 ,  B29C70/30 ,  B64C2001/0072 ,  B64F5/00 ,  Y02T50/43

Abstract: A pressure bulkhead comprises a plurality of material plies arranged one above the other, wherein each material ply contains reinforcing fibers embedded in a matrix material. The reinforcing fibers, in at least one first material ply are oriented in such a manner that their longitudinal axes lie in an angle range of ±2° about a radial direction of the pressure bulkhead.

公开(公告)号：US20160375535A1

公开(公告)日：2016-12-29

申请号：US15191721

申请日：2016-06-24

Applicant: Airbus Operations GmbH

Inventor： Paul Joern ,  Markus Mueller

IPC: B23Q11/00 ,  B23B45/00

CPC classification number: B23Q11/0071 ,  B23B35/00 ,  B23B2215/04 ,  B23B2226/275 ,  B23Q11/0053

Abstract: A drilling method for structural parts, in particular for carbon fiber composite structural parts, comprising the following method steps: providing a structural part and a collecting element; attaching the collecting element to a first side of the structural part opposite a drill point provided on a second side of the structural part, wherein a collecting portion of the collecting element is sealed off in a dust-tight manner from surroundings; drilling through the structural part from the second side of the structural part, at the drill point, using a drill, wherein the drill emerges from the structural part on the first side and enters the collecting portion of the collecting element, wherein drilling dust accumulating on the first side is collected by the collecting portion. A collecting element for a drilling method of this kind is disclosed.

Abstract translation: 结构部件的钻孔方法，特别是碳纤维复合结构部件的钻孔方法，包括以下方法步骤：提供结构部件和收集元件; 将所述收集元件附接到所述结构部件的与设置在所述结构部件的第二侧上的钻点相对的第一侧，其中所述收集元件的收集部分以防尘环境方式被密封; 在结构部分的第二侧穿过结构部分，在钻头处使用钻头，其中钻头从第一侧上的结构部件出来并进入收集元件的收集部分，其中钻出积聚在其上的灰尘 第一侧由收集部收集。 公开了一种用于这种钻孔方法的收集元件。

公开(公告)号：US09327821B2

公开(公告)日：2016-05-03

申请号：US13779432

申请日：2013-02-27

Applicant: AIRBUS OPERATIONS GMBH

Inventor： Pierre Zahlen ,  Ichwan Zuardy ,  Markus Mueller ,  Axel Herrmann

IPC: B64C1/18 ,  B64C1/06 ,  B64C1/12 ,  B64C1/00

CPC classification number: B64C1/18 ,  B64C1/00 ,  B64C1/068 ,  B64C1/12 ,  Y10T428/24612

Abstract: An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft.

Abstract translation: 飞机结构组件包括具有芯和外层的区域元件。 区域元件的第一表面至少在某些部分中相对于延伸穿过区域元件的芯的区域元件的假想中心区域呈凸形弯曲。 相比之下，与第一表面相对的区域元件的第二表面至少在某些部分上平行于延伸穿过区域元件的芯的区域元件的假想中心区域。 区域元件被配置为地板系统的地板面板的形式。 区域元件的第一或第二表面设计成在飞机结构组件的状态下安装在飞行器中时形成地板系统的可步行地板表面。